CN205273839U - Unmanned aerial vehicle with folding assembly - Google Patents
Unmanned aerial vehicle with folding assembly Download PDFInfo
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- CN205273839U CN205273839U CN201520978284.1U CN201520978284U CN205273839U CN 205273839 U CN205273839 U CN 205273839U CN 201520978284 U CN201520978284 U CN 201520978284U CN 205273839 U CN205273839 U CN 205273839U
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Abstract
The utility model discloses an unmanned aerial vehicle with folding assembly belongs to the unmanned air vehicle technique field, including fuselage, first rotor, second rotor, rotor shaft, a swivel connected coupler, the 2nd swivel connected coupler, folding assembly. Wherein, a swivel connected coupler includes: first motor and first dismantlement screw thread group, first rotor passes through first dismantlement screw thread group is connected with first motor is detachable, makes through rotatory installation or dismantlement between first rotor and the first motor can be realized to first rotor, the 2nd swivel connected coupler includes: second motor and second dismantlement screw thread group, the second rotor passes through second dismantlement screw thread group is connected with the second motor is detachable, makes through rotatory installation or dismantlement between second rotor and the second motor can be realized to the second rotor. The utility model has the characteristics of swiftly, portable and the operating efficiency is high.
Description
Technical field
The utility model belongs to unmanned air vehicle technique field, in particular to a kind of have Foldable assembly without man-machine.
Background technology
Unmanned spacecraft is called for short " without man-machine ", is the not manned aircraft utilizing wireless remote control equipment to handle with the programcontrol unit provided for oneself. Without cab on machine, but the equipment such as robot pilot, programcontrol unit, information collecting device are installed. On ground, naval vessels or machine tool remote-controlled station personnel by equipment such as radars, it is followed the tracks of, locates, remote control, remote measurement and digital transmission. Can take off as common aircraft under wireless remote control or launch with booster rocket, it is possible to take to by machine tool and throw in flight in the air.
Of the prior art without man-machine, usually it is fixed with a drive-motor in the end of rotor shaft, for usually adopting bolt to be directly fixed on drive-motor without the man-machine rotor taken off, and then drives rotor to rotate by drive-motor.
But, the mode of connection that this kind is directly bolted, make no matter to be arranged on drive-motor by rotor, or rotor is dismantled from drive-motor, all need to turn bolt by extraneous handle, and then complete the installation and removal work of rotor, particularly for many rotor wing unmanned aerial vehicles, its rotor quantity is multiple often, when needing some the rotors to many rotor wing unmanned aerial vehicles to install or dismantle, make installing/dismounting work very loaded down with trivial details, affect the operation efficiency of staff. simultaneously, prior art often adopts with rotor the mode being fixedly connected with without man-machine fuselage, make rotor relative to the state being in relative securement without man-machine fuselage, but the mode that this kind of fuselage is fixedly connected with rotor make without man-machine no matter be when flying operation or do not fly operation time, rotor is in open configuration all the time relative to fuselage, under this state, when without man-machine do not fly operation time, the rotor being under open configuration not only occupies parking space, simultaneously also very easily by other goods clashing and breaking extraneous, break, shorten the work-ing life without man-machine (rotor) greatly, and then bring, because rotor maintenance is frequent, the defect that maintenance cost is high.
Practical novel content
The utility model provide a kind of have Foldable assembly without man-machine, solve or part solves prior art when carrying out installing or dismantling for some rotors of many rotor wing unmanned aerial vehicles, installing/dismounting work is very loaded down with trivial details, affects the technological deficiency of staff's operation efficiency. , by Foldable assembly, rotor shaft and fuselage are rotationally connected meanwhile, overcome in prior art when without man-machine do not fly operation time, the oar being under open configuration not only occupies parking space, also very easily by other goods clashing and breaking extraneous, the technological deficiency that breaks.
The utility model provide a kind of have Foldable assembly without man-machine, comprise the rotor shaft that fuselage, at least four the first rotors two rotor identical with described first rotor quantity and described first rotor or described 2nd rotor quantity are identical; Described have also comprising without man-machine of Foldable assembly: first rotary connector identical with described first rotor quantity, described first rotor is rotatably connected with a described rotor shaft by described first rotary connector, described first rotary connector comprises: the first motor, described first motor comprises the first surface and the 2nd surface, and described first motor is fixed in described rotor shaft by described first surface; First dismounting thread set, described first rotor is rotatably connected with described first surface by described first dismounting thread set so that realize the installation or removal between described first rotor and described first motor by rotating described first rotor; Two rotary connector identical with described 2nd rotor quantity, described 2nd rotor is rotatably connected with a described rotor shaft by described 2nd rotary connector, described 2nd rotary connector comprises: the 2nd motor, described 2nd motor comprises the 3rd surface and the 4th surface, and described 2nd motor is fixed in described rotor shaft by described 3rd surface; 2nd dismounting thread set, described 2nd rotor is rotatably connected with described 3rd surface by described 2nd dismounting thread set so that realize the installation or removal between described 2nd rotor and described 2nd motor by rotating described 2nd rotor; The Foldable assembly identical with described first rotor quantity or described 2nd rotor quantity, a described rotor shaft is fixed on described fuselage by a described Foldable assembly rotationally so that described rotor shaft can be opened relative to described fuselage or shrink.
Optionally, described first dismounting thread set comprises: the first screw; 2nd screw; First screw buckle, the inwall of described first screw buckle is provided with the first internal thread, and the first screw has been offered in the bottom of described first screw buckle so that described first screw buckle is fixed on described first on the surface through described first screw by described first screw; First dismounting nut, the outer wall of described first dismounting nut is provided with the first outside screw, and described first dismounting nut top offered the 2nd screw so that described 2nd screw successively through described first rotor, described 2nd screw by described first dismounting nut be fixed on described first rotor; Wherein, described first internal thread and described first outside screw are suitable, and by the occlusion between described first internal thread and described first outside screw or separation, the corresponding installation realized between described first rotor and described first motor or dismounting.
Optionally, described first dismounting thread set also comprises: the first vibration damping sheet, described first vibration damping sheet offers the first through hole, and described first dismounting nut is fixed on described first rotor by described 2nd screw successively through described first through hole, described first rotor and the 2nd screw.
Optionally, described 2nd dismounting thread set comprises: the 3rd screw; 4th screw; 2nd screw buckle, the inwall of described 2nd screw buckle is provided with the 2nd internal thread, and the 3rd screw has been offered in the bottom of described 2nd screw buckle so that described 2nd screw buckle is fixed on the described 3rd on the surface through described 3rd screw by described 3rd screw; 2nd dismounting nut, the outer wall of described 2nd dismounting nut is provided with the 2nd outside screw, and described 2nd dismounting nut top offered the 4th screw so that described 4th screw successively through described 2nd rotor, described 3rd screw by described 2nd dismounting nut be fixed on described 2nd rotor; Wherein, described 2nd internal thread and described 2nd outside screw are suitable, and by the occlusion between described 2nd internal thread and described 2nd outside screw or separation, the corresponding installation realized between described 2nd rotor and described 3rd motor or dismounting.
Optionally, described first dismounting thread set also comprises: the 2nd vibration damping sheet, described 2nd vibration damping sheet offers the 2nd through hole, and described 2nd dismounting nut is fixed on described 2nd rotor by described 4th screw successively through described 2nd through hole, described 2nd rotor and the 4th screw.
Optionally, described Foldable assembly comprises: side plate part, and described side plate part is fixed on the end of described rotor shaft; Rotating part, described rotation part is fixed on described fuselage, and is rotationally connected with described side plate part, makes between described side plate part and described rotation part rotatable; Spacing part, described spacing part is fixed on described side plate part, to be positioned relative to the angle of rotation of described side plate part by described rotation part.
Optional: the end of described rotor shaft comprises the first side and two side faces, and the both sides, end being distributed in described rotor shaft of described first side and described two side faces symmetry; Described side plate part comprises: the first side plate, and described first side plate is fixed on described first side; 2nd side plate, described 2nd side plate is fixed on described two side faces; Wherein, a chute all offered by described first side plate and described first side plate, described spacing part is slided in described chute.
Optionally, described spacing part comprises: fixed link, and described fixed link is fixed between described first side plate and described 2nd side plate, and perpendicular with described first side plate and described 2nd side plate respectively, and has offered a sliding hole on described fixed link; Gag lever post, described gag lever post is placed in described chute, and is slidably connected with described chute; Pulling force bar, one end of described pulling force bar is fixedly connected with through described sliding hole with described gag lever post so that by pulling described pulling force bar to drive described gag lever post to slide in described chute.
Optionally, described rotation part comprises: the first pendulum ear, and described first pendulum ear has offered the first swing hole; 2nd pendulum ear, described 2nd pendulum ear is offered the two swing hole corresponding with described first swing hole; Fixing cylinder, one end of described fixing cylinder is fixed on described fuselage, and the other end is fixedly connected with described 2nd pendulum ear with described first pendulum ear respectively; Turning axle, described turning axle swings hole and described 2nd side plate through described first side plate, described first swing hole, the described 2nd successively, described side plate part and described rotation part to be rotationally connected.
Useful effect:
The utility model provide a kind of have Foldable assembly without man-machine, each first rotor is dismantled thread set by the one of correspondence first and is rotatably connected with the first surface of the first motor, make when carrying out installation or the dismantlement work of the first rotor, only need by rotating described first rotor, fastening or the separation between the first rotor and the first motor can be realized, each the 2nd rotor is dismantled thread set by the one of correspondence the 2nd and is rotatably connected with the 3rd surface of the 2nd motor, make when carrying out installation or the dismantlement work of the 2nd rotor, only need by rotating described 2nd rotor, fastening or the separation between the 2nd rotor and the 2nd motor can be realized, also namely without the need to can complete installation or the dismantlement work of rotor by extraneous operational tool (such as handle), have quick, the feature portable and operation efficiency is high. simultaneously, rotor shaft and fuselage are rotationally connected by the utility model by Foldable assembly, make rotor shaft can realize opening or indentation relative to flight equipment, overcome in prior art when flight equipment does not fly operation, the first rotor and/or the 2nd rotor that are under open configuration not only occupy parking space, simultaneously also very easily by other goods clashing and breaking extraneous, break, shorten the work-ing life of flight equipment greatly, and then bring, because oar maintenance is frequent, the defect that maintenance cost is high.
Accompanying drawing explanation
In order to be illustrated more clearly in the utility model embodiment or technical scheme of the prior art, it is briefly described to the accompanying drawing used required in embodiment below, apparently, accompanying drawing in the following describes is only embodiments more of the present utility model, for those of ordinary skill in the art, under the prerequisite not paying creative work, it is also possible to obtain other accompanying drawing according to these accompanying drawings.
Fig. 1 for the utility model embodiment one provide have Foldable assembly without man-machine one-piece construction schematic diagram;
Fig. 2 for Fig. 1 provide have Foldable assembly without man-machine side-view;
The connection relation that Fig. 3 is the first rotor in Fig. 1, the first dismounting thread set and rotor shaft splits structural side view;
Fig. 4 is the connection relation one-piece construction side-view of the first rotor in Fig. 3, the first dismounting thread set and rotor shaft;
Fig. 5 is the one-piece construction schematic diagram one of Foldable assembly in Fig. 1;
Fig. 6 is the vertical view of Foldable assembly in Fig. 5;
Fig. 7 is the one-piece construction schematic diagram two of Foldable assembly in Fig. 1;
Fig. 8 is the vertical view of Foldable assembly in Fig. 7;
Fig. 9 is the one-piece construction schematic diagram of slide assemblies in Fig. 1;
Figure 10 is the side-view of slide assemblies in Fig. 9;
Figure 11 for the utility model embodiment two provide have Foldable assembly without in man-machine, the connection relation of the first rotor, the 2nd rotor and rotor shaft splits schematic diagram.
Embodiment
Below in conjunction with the accompanying drawing in the utility model embodiment, the technical scheme in the utility model embodiment is clearly and completely described, it is clear that described embodiment is only the utility model part embodiment, instead of whole embodiments. Based on the embodiment in the utility model, other embodiments all that those of ordinary skill in the art obtain, all belong to the scope of the utility model protection; Wherein involved in this enforcement "and/or" keyword, represent and or two kinds of situations, in other words, A and/or B mentioned by the utility model embodiment, illustrate A and B, A or B two kinds of situations, describe three existing for A and B kind state, such as A and/or B, represent: only include A and do not comprise B; Only include B and do not comprise A; Comprise A and B.
Meanwhile, in the utility model embodiment, when assembly is called as " being fixed on " another assembly, it can directly on another assembly or can also there is assembly placed in the middle. When an assembly is considered as " connection " another assembly, it can be directly connected to another assembly or may there is assembly placed in the middle simultaneously. When an assembly is considered as " being arranged at " another assembly, it can be set directly on another assembly or may there is assembly placed in the middle simultaneously. Term " vertical ", " level ", "left", "right" and the similar statement used in the utility model embodiment, just in order to object is described, is not be intended to restriction the utility model.
The utility model provide a kind of have Foldable assembly without man-machine, each first rotor is dismantled thread set by the one of correspondence first and is rotatably connected with the first surface of the first motor, make when carrying out installation or the dismantlement work of the first rotor, only need by rotating described first rotor, fastening or the separation between the first rotor and the first motor can be realized, each the 2nd rotor is dismantled thread set by the one of correspondence the 2nd and is rotatably connected with the 3rd surface of the 2nd motor, make when carrying out installation or the dismantlement work of the 2nd rotor, only need by rotating described 2nd rotor, fastening or the separation between the 2nd rotor and the 2nd motor can be realized, also namely without the need to can complete installation or the dismantlement work of rotor by extraneous operational tool (such as handle), have quick, the feature portable and operation efficiency is high. simultaneously, rotor shaft and fuselage are rotationally connected by the utility model by Foldable assembly, make rotor shaft can realize opening or indentation relative to flight equipment, overcome in prior art when flight equipment does not fly operation, the first rotor and/or the 2nd rotor that are under open configuration not only occupy parking space, simultaneously also very easily by other goods clashing and breaking extraneous, break, shorten the work-ing life of flight equipment greatly, and then bring, because oar maintenance is frequent, the defect that maintenance cost is high.
Embodiment one
Specifically, referring to Fig. 1-2, what the utility model embodiment one provided a kind of has at least comprising without man-machine of Foldable assembly: Foldable assembly 5 that the first rotary connector 4 that the rotor shaft 3 that fuselage 1, at least four the first rotors 2 are identical with described first rotor 21 quantity is identical with described first rotor 21 quantity is identical with described first rotor 21 quantity, for settling slide assemblies 6 and the support 8 of battery.
Wherein, described first rotor 21 is connected by described first rotary connector 4 rotor shaft 3 described with is detachable. Please as shown in Figure 3-4, described first rotary connector 4 at least comprises: the first motor 41 and the first dismounting thread set 43. For driving, described first rotor 21 rotates described first motor 41, to drive fuselage 1 to fly. First motor 41 comprises the first surface 411 and the 2nd surface 412. In the utility model embodiment, can be as shown in Figure 3, it is the upper surface of the first motor 41 that first surface 411 can be understood as, and it is the lower surface of the first motor 41 that the 2nd surface 412 can be understood as, and described first motor 41 is fixed in described rotor shaft 3 by described first surface 411. Meanwhile, described first rotor 21 is connected with the first surface 411 of described first motor 41 is detachable by described first dismounting thread set 43.
For the mode of connection of the first rotor 21 and the first motor 41, both the first rotor 21 and the first motor 41, by setting up the first dismounting thread set 43, are threaded by the utility model embodiment one by the first dismounting thread set 43. Make in actual operation process when needs are to having when installing without man-machine multiple rotors or dismantle of Foldable assembly, only need to rotate described first rotor 21, as turned clockwise the first rotor 21 or be rotated counterclockwise the first rotor 21, the installation or removal between described first rotor 21 and described first motor 41 can be realized. Compared to traditional direct employing bolt, the first rotor 21 is fixed on the first motor 41, when the first rotor 21 is dismantled by needs from the first motor 41, or when installing, all need to turn bolt by extraneous handle, dismounting and the installation work of the first rotor 21 can be completed. And owing to being the individual component of Individual existence for connecting the standing bolt of the first rotor 21 and the first motor 41, when by handle turn bolt unloaded time, often due to the complicacy of execute-in-place environment, very easily cause the loss of standing bolt, and once standing bolt is lost, then just cannot complete the installation work of the first rotor 21 and the first motor 41, namely cause the serious consequence that flight equipment cannot fly. And the utility model embodiment, just by adopting the first dismounting thread set 43 both first rotor 21 and the first motor 41 to be threaded, make the two when installing or dismantle, without the need to by extraneous operational tool (such as handle), quick and convenient, have the advantages that operation efficiency is high.
For the first dismounting thread set 43, please continuing see Fig. 4, described first dismounting thread set 43 at least comprises: the first screw 431, the 2nd screw 432, first screw buckle 433 and the first dismounting nut 436. Wherein, the inwall of described first screw buckle 433 is provided with the first internal thread 434, and the bottom of described first screw buckle 433 offered the first screw 435 so that described first screw buckle 433 is fixed on the first surface 411 of described first motor 41 by described first screw 432 through described first screw 435. The outer wall of described first dismounting nut 436 is provided with first outside screw 437 suitable with described first internal thread 434, and described first dismounting nut 436 top offered the 2nd screw 438 so that described 2nd screw 432 successively through described first rotor 21, described 2nd screw 438 by described first dismounting nut 436 be fixed on described first rotor 21.
Wherein, the first screw buckle 433 is fixed on the first surface 411 of the first motor 41 by the first screw 431, and the first dismounting nut 436 is fixed on the first rotor 21 by the 2nd screw 432. And first the first internal thread 434 offered of the inwall of screw buckle 433, and the first outside screw 437 that the outer wall of the first dismounting nut 436 is offered mates completely, also namely can realize occlusion between the first internal thread 434 and the first outside screw 437 and lock. So just make, when the first rotor 21 is arranged in rotor shaft 3 by needs, owing to the first motor 41 is fixed on the end of rotor shaft 3, also it is about to the first rotor 21 and is arranged on the first motor 41. Now, only need manually to rotate the first rotor 21, first outside screw 437 is engaged mutually with the first internal thread 434, continue to rotate, then the locking of the first dismounting nut 436 and the first screw buckle 433 is realized, owing to the first dismounting nut 436 is fixed on the first rotor 21, the first screw buckle 433 is fixed on the first motor 41, and the locking also namely achieving the first rotor 21 and the first motor 41 (rotor shaft 3) is installed. And when disassembly is desired, now only needing reverse rotation first rotor 21, it is achieved the first outside screw 437 is separated with the first internal thread 434. There is swift to operate, feature easily.
It should be noted that, have Foldable assembly without man-machine in practical flight process, the sense of rotation of the first rotor 21 is for being rotated counterclockwise direction, now, itself it is the state being in constantly rotation due to the first rotor 21 in flight course, and itself also it is adopt to rotate to realize fastening mode of connection in the utility model embodiment between the first rotor 21 and the first motor 41. Such as, when the first rotor 21 is realize fastening therebetween by turning clockwise relative to the first motor 41, owing to normally rotating to be of the first rotor 21 in flight course is counterclockwise, now along with the counterclockwise normal of the first rotor 21 rotates, also namely the first rotor 21 is equivalent to the first motor 41 and has the driving being rotated counterclockwise. And could realize fastening therebetween by turning clockwise relative to the first motor 41 due to the first rotor 21, otherwise so when occurring that the first rotor 21 is be rotated counterclockwise relative to the first motor 41, namely the fastening relation between the first rotor 21 and the first motor 41 can be caused to occur loosening, even cause the first rotor 21 to fly away from the first motor 41 and cause the phenomenon without man-machine crash with Foldable assembly to occur.
Therefore, causing the fastening relation between the first rotor 21 and the first motor 41 to occur loosening to avoid many rotors flight equipment in flight course due to the first being normally rotated counterclockwise of rotor 21, the utility model embodiment rotates, by between the first rotor 21 and the first motor 41, the direction also being arranged to be rotated counterclockwise in the direction tightened. Namely, also the occlusion locking direction of first outside screw 437 set by outer wall of the first dismounting nut 436 and first internal thread 434 set by inwall of the first screw buckle 433 is also counterclockwise. So just make when the first rotor 21 relative to the first motor 41 be by be rotated counterclockwise realize fastening therebetween time, owing to normally rotating to be of the first rotor 21 in flight course is counterclockwise, now along with the counterclockwise normal of the first rotor 21 rotates, also namely the first rotor 21 is equivalent to the first motor 41 and also has the trend being rotated counterclockwise.
And due to the first rotor 21 be exactly could realize therebetween by being rotated counterclockwise fastening relative to the first motor 41, so on the one hand, effectively prevent when the first rotor 21 is realize occlusion locking by turning clockwise relative to the first motor 41, owing to normally rotating to be of the first rotor 21 causes the fastening relation between the first rotor 21 and the first motor 41 to occur loosening counterclockwise, the first rotor 21 is even caused to fly away from the first motor 41 and cause the technological deficiency without man-machine crash with Foldable assembly. On the other hand, due to the first rotor 21 itself also it is could realize therebetween by being rotated counterclockwise fastening relative to the first motor 4, when rotating along with the normal counterclockwise of the first rotor 21, and make the first rotor 21 be equivalent to the first motor 41 and also have the trend being rotated counterclockwise, now just also increase the first rotor 21 and the first motor 41 fastening relation therebetween, ensure that the normal safe of flight equipment flies, have the advantages that safety performance is high.
Further, please continue see Fig. 3-4, as described above, when described first dismounting nut 436 being fixed on described first rotor 21 through described first rotor 21, described 2nd screw 438 successively by the 2nd screw 432, due to have Foldable assembly without man-machine in flight course, external resistance factor suffered by first rotor 21 is more, such as air-flow, wind direction etc. This just makes the first rotor 21 in flight course bigger relative to the vibrations of the first motor 41 and/or rotor shaft 3, but, long-time vibrations can make the connection relation extremely unstable between the 2nd screw 432, first rotor 21 and the first dismounting nut 436 three, even cause the 2nd screw 432 to loosen, then cause security incident. Therefore, the utility model embodiment is by setting up the first vibration damping sheet 439, and offer the first through hole on described first vibration damping sheet 439, so that described first dismounting nut 437 is fixed on described first rotor 21 by described 2nd screw 432 successively through described first through hole, described first rotor 21 and the 2nd screw 438. As preferably, first vibration damping sheet 439 can be disk shape, to increase the contact area of the first vibration damping sheet 439 and the first rotor 21 upper surface, by the 2nd screw 432 by the first vibration damping sheet 439 and the first rotor 21 upper surface relative to fastening, to reduce the vibrations of the first rotor 21 relative to the first motor 41, it is to increase the safety and stability performance in flight course.
Fig. 3-6 is consulted in the lump incorporated by reference to Fig. 1-2, for the Foldable assembly 5 that the utility model embodiment one provides, a described rotor shaft 3 is fixed on described fuselage 1 by a described Foldable assembly 5 rotationally so that described rotor shaft 3 can be opened relative to described fuselage 1 or shrink. so just making in actual operation process, when flight equipment needs flight operation, then rotor shaft 3 is rotated relative to fuselage 1 by Foldable assembly, it is achieved rotor shaft 3 is in open configuration relative to fuselage 1. when flight equipment does not need flight operation, then rotor shaft 3 is rotated relative to fuselage 1 by Foldable assembly again, rotor shaft 3 is made to be in indentation state relative to described fuselage 1, overcome in prior art when flight equipment does not fly operation, the first rotor 21 and/or the rotor shaft 3 that are under open configuration not only occupy parking space, simultaneously also very easily by other goods clashing and breaking extraneous, break, shorten the work-ing life of flight equipment (the first rotor 21) greatly, and then bring, because of the keeping in repair frequent of the first rotor 21, the defect that maintenance cost is high.
Specifically, please as shown in Figure 5, described Foldable assembly 5 at least comprises: side plate part 51, rotation part 52 and spacing part 53.
Wherein, the end of described rotor shaft 3 away from that one end of the first rotor 21 is fixed in one end of described side plate part 51. The bottom of described rotation part 52 is fixed on described fuselage 1, and its top and described side plate part 51 are rotationally connected, and makes described side plate part 51 and described rotation part 52 point centered by tie point therebetween realize rotating. Described spacing part 53 is fixed on described side plate part 51 slidably, and is moved relative to described rotation part 52 by described spacing part 53 and positioned relative to the angle of rotation of described side plate part 51 by described rotation part 52. Such as, referring to shown in Fig. 5, now side plate part 51 and rotation part 52 vertical distribution, namely side plate part 51 is 90 �� relative to the angle of rotation part 52, and is realized the location of 90 �� of angles between the two by spacing part 53. For another example, referring to shown in Fig. 7, now side plate part 51 and rotation part 52 horizontal distribution, namely side plate part 51 is 0 �� relative to the angle of rotation part 52, and is realized the location of 0 �� of angle between the two by spacing part 53.
For side plate part 51, the principle of work that rotates between part 52 and spacing part 53 three, please following further described in:
For side plate part 51, comprise the first side plate 511 and the 2nd side plate 512, and the first side plate 511 and the 2nd side plate 512 are also all offered a chute 513 slided for spacing part 53. Wherein, the first side plate 511 is fixed on a side of rotor shaft 3 end, it is possible to understand that for being the first side of rotor shaft 3 end, the 2nd side plate 512 is fixed on another side of rotor shaft 3 end, it is possible to understand that for being the two side faces of rotor shaft 3 end. And the both sides, end being distributed in described rotor shaft 3 of described first side and described two side faces symmetry. So just make the first side plate 511 and the 2nd side plate 512 on the end being fixed on rotor shaft 3 in the way of being parallel to each other.
For spacing part 53, comprising: fixed link 531, gag lever post 532 and pulling force bar 533. Wherein, the two ends of described fixed link 531 are corresponding respectively to be fixed on the first side plate 511 and the 2nd side plate 512, make fixed link 531 between described first side plate 511 and described 2nd side plate 512, and perpendicular with described first side plate 511 and described 2nd side plate 512 respectively, and the middle position of described fixed link 531 is offered a sliding hole passed for pulling force bar 533. Described gag lever post 532 is laterally placed in described chute 513 so that slide in the axis direction that gag lever post 532 can prolong rotor shaft 3 in described chute 513. The sliding hole that one end of described pulling force bar 533 is offered on described fixed link 531, and be fixedly connected with described gag lever post 532 so that drive in chute 513 described in described gag lever post 532 by pulling described pulling force bar 533 and slide.
For rotating part 52, comprising: the first pendulum ear 521, the 2nd pendulum ear 522, fixing cylinder 523 and turning axle 524. Wherein, described first pendulum ear 521 has offered the first swing hole; Described 2nd pendulum ear 522 is offered the two swing hole corresponding with described first swing hole. And one end of described fixing cylinder 523 is fixed on described fuselage 1, the other end is fixedly connected with described 2nd pendulum ear 522 with described first pendulum ear 521 respectively. Described turning axle 524 swings hole and described 2nd side plate 522 through described first side plate 521, described first swing hole, the described 2nd successively, described side plate part 51 and described rotation part 52 to be rotationally connected.
Wherein, shown in accompanying drawing 5 and accompanying drawing 6 is rotate the schematic diagram that part 52 is in 90 �� of angles relative to side plate part 51, under this state, gag lever post 532 in chute 513 in the effect lower slip of pulling force bar 533 to the right (shown in Fig. 5 and Fig. 6 the right) of chute 513, now fix cylinder 523 and be in vertical state. Further can as shown in Figure 5, and what the first pendulum ear 521 was corresponding near the side of gag lever post 532 is provided with the first curvilinear portion, and described first curvilinear portion is circular arc shape, and what the side back to gag lever post 532 was corresponding is provided with the first screens, and described first screens is L-type. Identical, what the 2nd pendulum ear 522 was corresponding near the side of gag lever post 532 is provided with the 2nd curvilinear portion, and described 2nd curvilinear portion is circular arc shape, and what the side back to gag lever post 532 was corresponding is provided with the 2nd screens, and described 2nd screens is L-type.
Specifically, when rotating part 52 and be in 90 �� of angles relative to side plate part 51 (shown in accompanying drawing 5), now gag lever post 532 in chute 513 in the effect lower slip of pulling force bar 533 to the right of chute 513, also namely gag lever post 532 contacts with the first curvilinear portion and the 2nd curvilinear portion. When rotating part 52 and be in 0 �� of angle relative to side plate part 51 (shown in accompanying drawing 7), now gag lever post 532 slides to the left side of chute 513 in chute 513 under the effect of pulling force bar 533, until the first curvilinear portion and the 2nd curvilinear portion are in the lower section of gag lever post 532 completely. At this moment gag lever post 532 just drops down onto the first screens and the 2nd screens carries out spacing. Because now the first curvilinear portion and the 2nd curvilinear portion are upwards dug the stop caused by gag lever post 532, also namely limit the first pendulum ear 521 and the 2nd pendulum ear 522 moves up, then achieve side plate part 51 and rotate the horizontal location of part 52.
It should be noted that, in order to strengthen the automatic spacing function of Foldable assembly 5, it is achieved manually pull pulling force bar 533 can realize the spacing action between side plate part 51 and rotation part 52 without the need to operator. As preferably, being also provided with a spring 534 between the sliding hole offered in the middle of described fixed link 531 and described gag lever post 532, and described spring 534 is set on the outer wall of described pulling force bar 533.
As stated above, after setting up spring 534, when rotating part 52 and be in 90 �� of angles relative to side plate part 51 (shown in accompanying drawing 5), now gag lever post 532 slides into the right of chute 513 under the compression thrust of spring 534 in chute 513, and also namely gag lever post 532 contacts with the first curvilinear portion and the 2nd curvilinear portion. When rotation part 52 is in 0 �� of angle relative to side plate part 51 by needs (shown in accompanying drawing 7), now only need to overturn fixing cylinder 523, owing to the first curvilinear portion and the 2nd curvilinear portion are all in circular arc shape, therefore the first curvilinear portion and the 2nd curvilinear portion with gag lever post 532 contact process in overcome clockwise and slowly rotate in the compression of spring 534. When the first curvilinear portion and the 2nd curvilinear portion just climb over gag lever post 533, now gag lever post 533 is in the compression thrust of spring 534, gag lever post 533 is promoted to be repositioned to rapidly the first screens and the 2nd screens place, then restriction first pendulum ear 521 and the 2nd pendulum ear 522 move up, it is achieved the horizontal location of side plate part 51 and rotation part 52.
Further, Fig. 9-10 is consulted in the lump incorporated by reference to Fig. 1, the slide assemblies 6 that the utility model embodiment one provides, for settling battery 7, and described slide assemblies 6 is slidably connected with described fuselage 1, to slide relative to described fuselage 1, and realized dismounting or the installation of battery relative to the slip of fuselage 1 by slide assemblies 6.
Specifically, described slide assemblies 6 comprises: permanent seat 61, sliding support 62, card buckle 63.
Wherein, described permanent seat 61 is fixed on the bottom of described fuselage 1. The inside of described sliding support 62 is hollow structure, and the volume of the spatial volume of this hollow structure and battery 7 is suitable, for arrangement battery 7. And described sliding support 62 is fixed on described permanent seat 61 slidably. Described card button 63 is fixed on the end of described permanent seat 61, and is provided with one for stopping the projection 64 that battery 7 slides on described card button 63, to be skidded off from described sliding support 62 by the described protruding 64 described batteries 7 of stop.
As preferably, described sliding support can comprise: the first side frame 621, the 2nd side frame 622, the 3rd side frame 623 and slide plate 624. Wherein, described first side frame 621, the 2nd side frame 622 and the 3rd side frame 623 are vertical respectively to be fixed on described permanent seat 61, and described first side frame 621 and described 2nd side frame 622 oppose distribution, described 3rd side frame 623 and described protruding 64 opposition distributions, with the inside hollow structure by described first side frame 621, described 2nd side frame 622, described 3rd side frame 623 and the described protruding 64 described sliding supports of formation. The side that described first side frame 621 and described 2nd side frame 622 fix with described permanent seat 61, it is provided with a slide rail 67, described slide plate 624 is connected with described first side frame 621 and described 2nd side frame 622 slide rail by described slide rail 67, and then realizes slide plate 624 and slided relative to described first side frame 621 and described 2nd side frame 622 by described slide rail 67. Described battery is placed on described slide plate.
It should be noted that the lower section of described buckle 63, also it is provided with an elastic button 65. By pressing described elastic button 65, it is achieved described protruding 64 open or clamp. In card button 3, elastic button 65 structure can be similar to the structures such as hair clip of the prior art, folder herein. When battery 7 is fixed in slide assemblies 6 by needs, only need to press downwards elastic button 65, open protruding 64, then slide plate 624 is outwards skidded off relative to sliding support, after battery 7 is fixed on slide plate 624, relative to sliding support slid inward slide plate 624, loosening elastic button 65, projection is close to battery 7 to be clamped. Achieve the firm installation of battery 7 in the unmanned plane during flying process with Foldable assembly, there is feature simple to operate, convenient disassembly.
In addition, what what the utility model embodiment one provided had a Foldable assembly also comprises a support 8 without man-machine, and this support 8 can be made up of 2 T-shaped framves, namely comprises the first T-shaped frame 81 and the 2nd T-shaped frame 82. Wherein, the vertical end of the first T-shaped frame 81 and the vertical end of the 2nd T-shaped frame 82 are fixed on the bottom of fuselage 1, and stablize chessboard by the transverse end formation one of the transverse end of the first T-shaped frame 81 and the 2nd T-shaped frame 82 and support to have the advantages that stationary performance is high to during to be landed by flight equipment.
Just as shown in Figure 1-2, the utility model embodiment one provide have Foldable assembly without man-machine can be six rotors have Foldable assembly without man-machine, both comprised 6 the first rotors 21. Certainly, it will be appreciated by those skilled in the art that, six rotors have Foldable assembly without man-machine be only a kind of enforcement mode of the utility model embodiment, not limitation, in other words, also all it is applicable to the utility model embodiment one for what four rotors, eight rotors, 12 rotors etc. had a Foldable assembly without man-machine.
Embodiment two
Using 12 rotors have Foldable assembly without man-machine as embodiment two of the present utility model, because six rotors shown in Fig. 1-2 have Foldable assembly without man-machine, what it adopted is all single oar single shaft, and also namely each rotor shaft 3 is equipped with first motor 41 and first rotor 21. When six rotors shown in Fig. 1-2 have Foldable assembly without man-machine, when its each rotor shaft 3 is equipped with two motors and two rotors, also coaxial (two the shared rotor shaft 3 of rotors of two oar are namely all adopted, form the 2nd rotary connector by the 2nd motor 42 and the 2nd rotor 22), namely formed 12 rotors have Foldable assembly without man-machine. Can be as shown in figure 11.
Now, rotor shaft 3 for connect fuselage 1 one end as coupling end 32, be rotationally connected by Foldable assembly 5 and fuselage 1. Rotor shaft 3 for connect rotor one end as coaxial end 21, this coaxial end 31 can comprise the first end face 311 (upper surface), biend 312 (lower surface) and accommodating space 313. In two oar coaxial construction, a rotor group 2 is formed by the first rotor 21 and the 2nd rotor 22, and first rotor 21 be fixed on the first end face 311 of coaxial end 31 rotationally by the first motor 41, on the biend 312 of the 2nd rotor 22 by the 2nd motor 42 coaxial end 31 rotationally. It is fixed in accommodating space 313 for connecting the electricity tune of the first motor 41 and the 2nd motor 42 respectively, described first motor 41 and described 2nd motor 42 are adjusted by described electricity respectively be connected with the flight controlling system in fuselage 1, and then realize described flight controlling system and rotated by described first rotor 21 of driving of described first motor 41 correspondence, and rotated by described 2nd rotor 22 of driving of described 2nd motor 42 correspondence.
Obviously, it will be appreciated by those skilled in the art that, in two oar coaxial construction, first rotor 21 is rotatably connected with the first surface 411 of the first motor 41 by the first dismounting thread set 43,2nd rotor 22 is also rotatably connected with the 3rd surface 421 of the 2nd motor 42 (the 2nd dismantles the 2nd rotary connector that thread set and the 2nd motor 42 form in the present embodiment two) by the 2nd dismounting thread set, and the biend 312 of the 4th surface 422 of the 2nd motor axle head 31 together is fixedly connected with. First rotor 21 is rotatably connected with the first surface 411 of the first motor 41 by the first dismounting thread set 43, at above-mentioned detail, repeats no more herein. Only the 2nd rotor 22 is rotatably connected with the 3rd surface 421 of the 2nd motor 42 by the 2nd dismounting thread set below and elaborates.
The utility model embodiment two, please continue see Figure 11, corresponding with the first dismounting thread set 43, and described 2nd dismounting thread set at least comprises: the 3rd screw 441, the 4th screw 442, the 2nd screw buckle 443 and the 2nd dismounting nut 446. Wherein, the inwall of described 2nd screw buckle 443 is provided with the 2nd internal thread, and the bottom of described 2nd screw buckle 443 offered the 3rd screw so that described 2nd screw buckle 443 is fixed on the 3rd surface 421 of described 2nd motor 42 by described 3rd screw 441 through described 3rd screw. The outer wall of described 2nd dismounting nut 446 is provided with two outside screw suitable with described 2nd internal thread, and described 2nd dismounting nut 446 top offered the 4th screw so that described 4th screw 442 successively through described 2nd rotor 22, described 4th screw by described 2nd dismounting nut 446 be fixed on described 2nd rotor 22.
Identical with the first dismounting thread set 43 internal structure, the 2nd screw buckle 443 is fixed on the 3rd surface 421 of the 2nd motor 42 by the 3rd screw 441, and the 2nd dismounting nut 446 is fixed on the 2nd rotor 22 by the 4th screw 442. And the 2nd the 2nd outside screw offered of the outer wall of the 2nd internal thread offered of the inwall of screw buckle 443 and the 2nd dismounting nut 446 mate completely, also namely can realize occlusion between the 2nd internal thread and the 2nd outside screw and lock. So just make, when the 2nd rotor 22 is arranged in rotor shaft 3 by needs, owing to the 2nd motor 42 is fixed on the end of rotor shaft 3, also it is about to the 2nd rotor 22 and is arranged on the 2nd motor 42. Now, only need manually to rotate the 2nd rotor 22,2nd outside screw is engaged mutually with the 2nd internal thread, continue to rotate, then the locking of the 2nd dismounting nut 446 and the 2nd screw buckle 443 is realized, owing to the 2nd dismounting nut 446 is fixed on the 2nd rotor 22, the 2nd screw buckle 443 is fixed on the 2nd motor 42, and the locking also namely achieving the 2nd rotor 22 and the 2nd motor 42 (rotor shaft 3) is installed. And when disassembly is desired, now only needing reverse rotation the 2nd rotor 22, it is achieved the 2nd outside screw is separated with the 2nd internal thread. There is swift to operate, feature easily.
It is specifically intended that, in the utility model embodiment two, the sense of rotation of the first rotor 21 is counterclockwise, then the sense of rotation of the 2nd rotor 22 is clockwise direction, because in single oar rotary course, also the rotation of i.e. the first rotor 21, can produce corresponding torsion, it is necessary to torsion that the antagonism of corresponding thrust produces makes its complete machine balance to rely on the tail-rotor on flight equipment to produce. But, in the utility model embodiment two, two contrary water screws taked by two oar (the first rotor 21 and the 2nd rotor 22), namely rotate towards counterclockwise by the first rotor 21,2nd rotor 22 rotates towards clockwise direction, make two rotors produce two contrary torsion of direction, directly cancel out each other. Making the stability of flight equipment better so on the one hand, direction easily controls; Structure is simple on the other hand, reduces the generation of safety failure; Another further aspect, the power of flight equipment flight is bigger, and bearing capacity is more, has the feature of wide adaptability.
It should be noted that equally, what the utility model embodiment two provided have Foldable assembly without man-machine in practical flight process, the sense of rotation of the 2nd rotor 22 is the direction that turns clockwise, now, itself also it is the state being in constantly rotation due to the 2nd rotor 22 in flight course, and itself also it is adopt to rotate to realize fastening mode of connection in the utility model embodiment two between the 2nd rotor 22 and the 2nd motor 42. Such as, when the 2nd rotor 22 relative to the 2nd motor 42 be by be rotated counterclockwise realize fastening therebetween time, owing to normally rotating to be of the 2nd rotor 22 in flight course is clockwise, now along with the clockwise normal of the 2nd rotor 22 rotates, also namely the 2nd rotor 22 is equivalent to the 2nd motor 42 and has the driving turned clockwise. And due to the 2nd rotor 22 relative to the 2nd motor 42 by be rotated counterclockwise could realize fastening therebetween, otherwise so when occurring that the 2nd rotor 22 is turn clockwise relative to the 2nd motor 42, namely the fastening relation between the 2nd rotor 22 and the 2nd motor 42 can be caused to occur loosening, even cause the 2nd rotor 22 to fly away from the 2nd motor 42 and cause the phenomenon without man-machine crash with Foldable assembly to occur.
Therefore, causing the fastening relation between the 2nd rotor 22 and the 2nd motor 42 to occur loosening to avoid many rotors flight equipment in flight course due to the 2nd normally turning clockwise of rotor 22, the utility model embodiment two will rotate the direction also being arranged to turn clockwise in the direction tightened between the 2nd rotor 22 and the 2nd motor 42. Namely, also the occlusion locking direction of the 2nd outside screw set by outer wall of the 2nd dismounting nut 446 and the 2nd internal thread set by inwall of the 2nd screw buckle 443 is also clockwise direction. So just make when the 2nd rotor 22 is realize fastening therebetween by turning clockwise relative to the 2nd motor 42, owing to normally rotating to be of the 2nd rotor 22 in flight course is clockwise, now along with the clockwise normal of the 2nd rotor 22 rotates, also namely the 2nd rotor 22 is equivalent to the 2nd motor 42 and also has the trend turned clockwise.
And due to the 2nd rotor 22 be exactly could realize therebetween by turning clockwise fastening relative to the 2nd motor 42, so on the one hand, effectively prevent when the 2nd rotor 22 is by being rotated counterclockwise realization occlusion locking relative to the 2nd motor 42, owing to normally rotating to be of the 2nd rotor 22 causes the fastening relation between the 2nd rotor 22 and the 2nd motor 42 to occur loosening clockwise, the 2nd rotor 22 is even caused to fly away from the 2nd motor 42 and cause the technological deficiency without man-machine crash with Foldable assembly. On the other hand, due to the 2nd rotor 22 itself also it is could realize therebetween by turning clockwise fastening relative to the 2nd motor 42, when rotating along with the normal clockwise of the 2nd rotor 22, and make the 2nd rotor 22 be equivalent to the 2nd motor 42 and also have the trend turned clockwise, now just also increase the 2nd rotor 22 and the 2nd motor 42 fastening relation therebetween, ensure that the normal safe of flight equipment flies, have the advantages that safety performance is high.
Further, please continue see Figure 11, as described above, when described 2nd dismounting nut 446 being fixed on described 2nd rotor 22 through described 2nd rotor 22, described 4th screw successively by the 4th screw 442, due to have Foldable assembly without man-machine in flight course, external resistance factor suffered by 2nd rotor 22 is more, such as air-flow, wind direction etc. This just makes the 2nd rotor 22 in flight course bigger relative to the vibrations of the 2nd motor 42 and/or rotor shaft 3, but, long-time vibrations can make the connection relation extremely unstable between the 4th screw 442, the 2nd rotor 22 and the 2nd dismounting nut 446 three, even cause the 4th screw 442 to loosen, then cause security incident. Therefore, the utility model embodiment two is by setting up the 2nd vibration damping sheet 449, and offer the 2nd through hole on described 2nd vibration damping sheet 449, so that described 2nd dismounting nut 446 is fixed on described 2nd rotor 22 by described 4th screw 442 successively through described 2nd through hole, described 2nd rotor 22 and the 4th screw. As preferably, 2nd vibration damping sheet 449 can be disk shape, to increase the 2nd vibration damping sheet 449 and the contact area of the 2nd rotor 22 lower surface, by the 4th screw 442 by the 2nd vibration damping sheet 449 and the 2nd rotor 22 lower surface relative to fastening, to reduce the vibrations of the 2nd rotor 22 relative to the 2nd motor 42, it is to increase the safety and stability performance in flight course.
The utility model embodiment two and the utility model embodiment one are except the 2nd rotor 22 and the 2nd dismounting thread set, remaining component as: it is all completely identical that the first rotor 21, first dismantles thread set 43, Foldable assembly 5, slide assemblies 6, support 8 etc., no longer repeating for embodiment two, in embodiment two, not detailed part can consult embodiment one herein.
The utility model provide have Foldable assembly without man-machine, its useful effect as follows described in:
1., each first rotor 21 in the utility model is connected with the first surface 411 of the first motor 41 is detachable by corresponding one first dismounting thread set 43, make when carrying out installation or the dismantlement work of the first rotor 21, only need by rotating described first rotor 21, fastening or the separation between the first rotor 21 and the first motor 41 can be realized, also namely without the need to can complete installation or the dismantlement work of rotor by extraneous operational tool (such as handle), there is quick, portable and that operation efficiency is high feature;
2., the utility model is by being designed to identical with the direction that the first rotor 21 normally rotates by the first outside screw 437 with the occlusion locking direction of the first internal thread 434, namely also it is counterclockwise, so on the one hand, effectively prevent the fastening relation between the first rotor 21 and the first motor 41 to occur loosening, even cause the first rotor 21 to fly away from the first motor 41 and cause the technological deficiency without man-machine crash with Foldable assembly; On the other hand, just also increase the first rotor 21 and the first motor 41 fastening relation therebetween, ensure that the normal safe of flight equipment flies, have the advantages that safety performance is high;
3., the utility model is by setting up the first vibration damping sheet 439, and by the 2nd screw 432 by the first vibration damping sheet 439 and the first rotor 21 upper surface relative to fastening, to reduce the vibrations of the first rotor 21 relative to the first motor 41, it is to increase the safety and stability performance in flight course;
4., in the utility model, rotor shaft 3 is rotated relative to fuselage 1 by Foldable assembly 5, realize rotor shaft 3 to be in relative to fuselage 1 and open or indentation state, overcome in prior art when flight equipment does not fly operation, the first rotor 21 and/or the rotor shaft 3 that are under open configuration not only occupy parking space, simultaneously also very easily by other goods clashing and breaking extraneous, break, shorten the work-ing life of flight equipment (the first rotor 21) greatly, and then bring, because of the keeping in repair frequent of the first rotor 21, the defect that maintenance cost is high;
5., the utility model is by arranging slide assemblies 6, when battery 7 is fixed in slide assemblies 6 by needs, only need to press downwards elastic button 65, open protruding 64, then slide plate 624 is outwards skidded off relative to sliding support, after battery 7 is fixed on slide plate 624, relative to sliding support slid inward slide plate 624, loosen elastic button 65, projection is close to battery 7 to be clamped, achieve the firm installation of battery 7 in the unmanned plane during flying process with Foldable assembly, there is feature simple to operate, convenient disassembly.
Although having described preferred embodiment of the present utility model, but those skilled in the art once the substantially creative concept of cicada, then these embodiments can be made other change and amendment. Therefore, it is intended that the appended claims shall be construed comprise preferred embodiment and fall into all changes and the amendment of the utility model scope.
Obviously, the utility model can be carried out various change and modification and not depart from spirit and scope of the present utility model by the technician of this area. Like this, if these amendments of the present utility model and modification belong within the scope of the utility model claim and equivalent technologies thereof, then the utility model also is intended to comprise these change and modification.
Claims (9)
1. one kind have Foldable assembly without man-machine, comprise the rotor shaft that fuselage, at least four the first rotors two rotor identical with described first rotor quantity and described first rotor or described 2nd rotor quantity are identical; It is characterized in that, described in there is also comprising without man-machine of Foldable assembly:
First rotary connector identical with described first rotor quantity, described first rotor is rotatably connected with a described rotor shaft by described first rotary connector, and described first rotary connector comprises:
First motor, described first motor comprises the first surface and the 2nd surface, and described first motor is fixed in described rotor shaft by described first surface;
First dismounting thread set, described first rotor is rotatably connected with described first surface by described first dismounting thread set so that realize the installation or removal between described first rotor and described first motor by rotating described first rotor;
Two rotary connector identical with described 2nd rotor quantity, described 2nd rotor is rotatably connected with a described rotor shaft by described 2nd rotary connector, and described 2nd rotary connector comprises:
2nd motor, described 2nd motor comprises the 3rd surface and the 4th surface, and described 2nd motor is fixed in described rotor shaft by described 3rd surface;
2nd dismounting thread set, described 2nd rotor is rotatably connected with described 3rd surface by described 2nd dismounting thread set so that realize the installation or removal between described 2nd rotor and described 2nd motor by rotating described 2nd rotor;
The Foldable assembly identical with described first rotor quantity or described 2nd rotor quantity, a described rotor shaft is fixed on described fuselage by a described Foldable assembly rotationally so that described rotor shaft can be opened relative to described fuselage or shrink.
2. have as claimed in claim 1 Foldable assembly without man-machine, it is characterised in that, described first dismounting thread set comprises:
First screw;
2nd screw;
First screw buckle, the inwall of described first screw buckle is provided with the first internal thread, and the first screw has been offered in the bottom of described first screw buckle so that described first screw buckle is fixed on described first on the surface through described first screw by described first screw;
First dismounting nut, the outer wall of described first dismounting nut is provided with the first outside screw, and described first dismounting nut top offered the 2nd screw so that described 2nd screw successively through described first rotor, described 2nd screw by described first dismounting nut be fixed on described first rotor;
Wherein, described first internal thread and described first outside screw are suitable, and by the occlusion between described first internal thread and described first outside screw or separation, the corresponding installation realized between described first rotor and described first motor or dismounting.
3. have as claimed in claim 2 Foldable assembly without man-machine, it is characterised in that, described first dismounting thread set also comprises:
First vibration damping sheet, described first vibration damping sheet has offered the first through hole, and described first dismounting nut is fixed on described first rotor by described 2nd screw successively through described first through hole, described first rotor and the 2nd screw.
4. have as claimed in claim 1 Foldable assembly without man-machine, it is characterised in that, described 2nd dismounting thread set comprises:
3rd screw;
4th screw;
2nd screw buckle, the inwall of described 2nd screw buckle is provided with the 2nd internal thread, and the 3rd screw has been offered in the bottom of described 2nd screw buckle so that described 2nd screw buckle is fixed on the described 3rd on the surface through described 3rd screw by described 3rd screw;
2nd dismounting nut, the outer wall of described 2nd dismounting nut is provided with the 2nd outside screw, and described 2nd dismounting nut top offered the 4th screw so that described 4th screw successively through described 2nd rotor, described 3rd screw by described 2nd dismounting nut be fixed on described 2nd rotor;
Wherein, described 2nd internal thread and described 2nd outside screw are suitable, and by the occlusion between described 2nd internal thread and described 2nd outside screw or separation, the corresponding installation realized between described 2nd rotor and described 2nd motor or dismounting.
5. have as claimed in claim 4 Foldable assembly without man-machine, it is characterised in that, described first dismounting thread set also comprises:
2nd vibration damping sheet, described 2nd vibration damping sheet has offered the 2nd through hole, and described 2nd dismounting nut is fixed on described 2nd rotor by described 4th screw successively through described 2nd through hole, described 2nd rotor and the 4th screw.
6. have as claimed in claim 1 Foldable assembly without man-machine, it is characterised in that, described Foldable assembly comprises:
Side plate part, described side plate part is fixed on the end of described rotor shaft;
Rotating part, described rotation part is fixed on described fuselage, and is rotationally connected with described side plate part, makes between described side plate part and described rotation part rotatable;
Spacing part, described spacing part is fixed on described side plate part, to be positioned relative to the angle of rotation of described side plate part by described rotation part.
7. have as claimed in claim 6 Foldable assembly without man-machine, it is characterised in that:
The end of described rotor shaft comprises the first side and two side faces, and the both sides, end being distributed in described rotor shaft of described first side and described two side faces symmetry;
Described side plate part comprises:
First side plate, described first side plate is fixed on described first side;
2nd side plate, described 2nd side plate is fixed on described two side faces;
Wherein, a chute all offered by described first side plate and described first side plate, described spacing part is slided in described chute.
8. have as claimed in claim 7 Foldable assembly without man-machine, it is characterised in that, described spacing part comprises:
Fixed link, described fixed link is fixed between described first side plate and described 2nd side plate, and perpendicular with described first side plate and described 2nd side plate respectively, and has offered a sliding hole on described fixed link;
Gag lever post, described gag lever post is placed in described chute, and is slidably connected with described chute;
Pulling force bar, one end of described pulling force bar is fixedly connected with through described sliding hole with described gag lever post so that by pulling described pulling force bar to drive described gag lever post to slide in described chute.
9. as described in item as arbitrary in claim 7-8 have Foldable assembly without man-machine, it is characterised in that, described rotation part comprises:
First pendulum ear, described first pendulum ear has offered the first swing hole;
2nd pendulum ear, described 2nd pendulum ear is offered the two swing hole corresponding with described first swing hole;
Fixing cylinder, one end of described fixing cylinder is fixed on described fuselage, and the other end is fixedly connected with described 2nd pendulum ear with described first pendulum ear respectively;
Turning axle, described turning axle swings hole and described 2nd side plate through described first side plate, described first swing hole, the described 2nd successively, described side plate part and described rotation part to be rotationally connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520978284.1U CN205273839U (en) | 2015-11-30 | 2015-11-30 | Unmanned aerial vehicle with folding assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520978284.1U CN205273839U (en) | 2015-11-30 | 2015-11-30 | Unmanned aerial vehicle with folding assembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205273839U true CN205273839U (en) | 2016-06-01 |
Family
ID=56058440
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520978284.1U Expired - Fee Related CN205273839U (en) | 2015-11-30 | 2015-11-30 | Unmanned aerial vehicle with folding assembly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205273839U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105366032A (en) * | 2015-11-30 | 2016-03-02 | 湖北易瓦特科技股份有限公司 | Unmanned aerial vehicle with folding assemblies |
| CN106741943A (en) * | 2016-12-23 | 2017-05-31 | 歌尔科技有限公司 | A kind of unmanned plane |
| CN107323661A (en) * | 2017-07-03 | 2017-11-07 | 湖北龙翼机器人有限公司 | A kind of axle aircraft of multifunctional portable six |
| CN107380464A (en) * | 2017-07-28 | 2017-11-24 | 长春草莓科技有限公司 | A kind of unmanned plane battery rotary formula changes structure |
| CN108513555A (en) * | 2017-02-24 | 2018-09-07 | 深圳市大疆创新科技有限公司 | Foldable rack, rack components and unmanned vehicle |
| RU2790211C1 (en) * | 2022-09-24 | 2023-02-15 | Ооо "Финко" | Folding multicopter |
-
2015
- 2015-11-30 CN CN201520978284.1U patent/CN205273839U/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105366032A (en) * | 2015-11-30 | 2016-03-02 | 湖北易瓦特科技股份有限公司 | Unmanned aerial vehicle with folding assemblies |
| CN105366032B (en) * | 2015-11-30 | 2018-12-18 | 易瓦特科技股份公司 | Unmanned plane with foldable assembly |
| CN106741943A (en) * | 2016-12-23 | 2017-05-31 | 歌尔科技有限公司 | A kind of unmanned plane |
| CN106741943B (en) * | 2016-12-23 | 2023-10-20 | 歌尔科技有限公司 | Unmanned aerial vehicle |
| CN108513555A (en) * | 2017-02-24 | 2018-09-07 | 深圳市大疆创新科技有限公司 | Foldable rack, rack components and unmanned vehicle |
| CN107323661A (en) * | 2017-07-03 | 2017-11-07 | 湖北龙翼机器人有限公司 | A kind of axle aircraft of multifunctional portable six |
| CN107380464A (en) * | 2017-07-28 | 2017-11-24 | 长春草莓科技有限公司 | A kind of unmanned plane battery rotary formula changes structure |
| CN107380464B (en) * | 2017-07-28 | 2023-08-04 | 深圳草莓创新技术有限公司 | Unmanned aerial vehicle battery rotation type changes structure |
| RU2790211C1 (en) * | 2022-09-24 | 2023-02-15 | Ооо "Финко" | Folding multicopter |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C56 | Change in the name or address of the patentee | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 430000 Hubei province Wuhan City Jiang'an District Lake Street Bridge Road No. 5 Building 1 layer 4 Patentee after: Easy Technology Co Ltd Address before: 430000 Hubei province Wuhan City Jiang'an District Lake Street Bridge Road No. 5 Building 1 layer 4 Patentee before: EWATT CO., LTD. |
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| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160601 Termination date: 20181130 |